CN206125423U - VTOL fixed wing uavs with power device verts - Google Patents
VTOL fixed wing uavs with power device verts Download PDFInfo
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- CN206125423U CN206125423U CN201621167766.XU CN201621167766U CN206125423U CN 206125423 U CN206125423 U CN 206125423U CN 201621167766 U CN201621167766 U CN 201621167766U CN 206125423 U CN206125423 U CN 206125423U
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Abstract
The utility model relates to a VTOL fixed wing uavs with power device verts relates to the fixed wing uavs field. A VTOL unmanned aerial vehicle who has the structure power device that verts, including fuselage, wing, support arm, rotor power device system and fin. Under the VTOL mode, the four rotor power device of group of symmetry installation on the support arm are for unmanned aerial vehicle provides the power in the vertical direction, arrive behind the take the altitude through vert two screws of fuselage front end both sides of the structure of verting, and the rotational speed that reduces by two screws of wing rear side keeps the perpendicular lift component of two screws of its lift and front side balanced, and messenger unmanned aerial vehicle switches over to stationary vane flight mode. The utility model discloses it has increased effectual wing area to the requirement of VTOL with the big long flight time of load, the current VTOL aircraft of solution in VTOL structural configuration's limitation to have satisfied unmanned aerial vehicle simultaneously, and flight efficiency improves greatly.
Description
Technical field
The utility model is related to fixed-wing unmanned plane field, and specially a kind of VTOL with the power set that vert is consolidated
Determine wing unmanned plane.
Background technology
The accurate definition of vertically taking off and landing flyer (VTOL) is：Can be taken off with zero velocity/be landed, possess hovering ability,
And can the horizontal flight in the way of fixed wing aircraft.Compared with conventional airplane, vertically taking off and landing flyer to runway without dependence, and have
There is the advantage that can be hovered；Compared with conventional helicopters, vertically taking off and landing flyer has much higher forward flight speed, and with bigger
Voyage.Just because of possessing these advantages, vertically taking off and landing flyer is particularly suited for needing hovering or has special to landing site
The occasion of requirement.
Unmanned plane is typically divided into fixed-wing unmanned plane and rotary wings unmanned plane, wherein fixed-wing unmanned plane, by fixation
Relative motion between the wing and air produces lift, with long boat when, speed is fast, flight efficiency is high the characteristics of, be capable of achieving long boat
When big load flight.But meanwhile, in prior art, fixed-wing unmanned plane has the drawback that：Need special open place
For landing of taking off, and hovering cannot be realized.The rotation that rotary wings unmanned plane passes through rotary wings, with air relative motion is produced
Produce lift, with control precisely, little is required to landing site the features such as, be capable of achieving VTOL, but flight efficiency is low continuous
ETS estimated time of sailing is short, it is impossible to fly when realizing that big load length is navigated.
Existing vertically taking off and landing flyer is mostly using the VTOL that the control such as single shaft, twin shaft or three axles is very difficult
Topology layout form, not only stability and reliability are all difficult to ensure that during VTOL pattern, and because it is by the way of
The structure that aircraft can be caused is different from generally conventional fixed wing aircraft, excessively complicated, badly influences the gas under fixed-wing pattern
Dynamic layout, so as to have a strong impact on flight quality during flat flying.Another aspect, existing VTOL aircraft it is most of due to
Its structure design is limited, and is had no idea using the very big span, so as to increase effective wing area so that its flight effect
Rate cannot be improved, and voyage is compared or differed greatly with traditional fixed wing aircraft.So, only as far as possible using ripe gyroplane
Model layout's form and in the case of not affecting conventional fixed-wing aircraft layout structure, accomplishes VTOL function, could be maximum
The performance of the various aspects of vertically taking off and landing flyer is improved in degree.
Utility model content
Cannot be while the contradiction between requiring when meeting VTOL and big load length boat, sheet in solve prior art
Utility model provides a kind of VUAV with the structural dynamic device that verts, and specifically includes：Fuselage, wing,
Brace, rotor power device and empennage.
Described fuselage is fixed wing aircraft layout with wing；
Described fuselage is hollow housing structure, fuselage interior arrangement cargo compartment, air environment, battery and beam and
Reinforcing frame；Described air environment includes flight control panel, electron speed regulator and sensing data terminal；Fuselage side is
The mounting interface of wing；Described battery is polymer Li-ion battery；The front portion of fuselage is provided with pitot；On afterbody
One group of rotor power device is installed.
Described wing is fixed-wing aerofoil profile, and wing is hollow type structure, inside arrangement rib and girder construction；In unmanned plane
Both sides wing lower section is respectively installed by a piece support arm；The afterbody of two support arms is fixedly connected empennage.
Four groups of rotor power devices are symmetrically installed on described support arm, wherein two groups of rotor power devices are located at support arm
Leading edge, constitute the power set that vert described in the utility model；Other two groups of rotor power devices be located at wing and empennage it
Between support arm on；The geometric center of four groups of rotor power devices overlaps with the position of centre of gravity of whole unmanned plane.
Described empennage is reverse V-shaped.
Move five groups of described rotor power devices, part when lift when VTOL is provided for unmanned plane and cruise
Power.Every group of rotor power device includes a brushless electric machine and a carbon fiber spiral oar；Described brushless electric machine is outer rotor
Brshless DC motor, on the support arm being fixed on below wing using screw or fuselage, is controlled by air environment, by
Battery provides the energy；Described carbon fiber spiral oar includes propeller hub, blade and engine.
The utility model provides a kind of VTOL fixed-wing unmanned plane with the power set that vert, including five groups of rotors
Power set, two groups of rotor power devices therein, in support arm leading edge, can coaxially be verted by structure setting of verting；Two groups of rotations
Wing power set are located on the support arm between wing and empennage, there is provided vertical lift；Last group of rotor power device is located at
Afterbody, there is provided forward thrust.Under VTOL pattern, four groups of rotor power devices on support arm are provided in vertical direction
Power, reach certain altitude hypsokinesis and turn two screws of front fuselage both sides, reduce two screws on rear side of wing
Rotating speed keeps the vertical lift component balance of its lift and the screw of front side two, so that unmanned plane switches to fixed-wing flight
Pattern.
The utility model has the advantage of：With reference to the characteristics of existing fixed-wing unmanned plane and rotary wings unmanned plane, this is realized
A kind of VTOL fixed-wing unmanned plane with the power set that vert that utility model is proposed, while meeting unmanned plane to hanging down
Requirement when straight landing and big load length are navigated, solves limitation of the existing vertically taking off and landing flyer in VTOL topology layout, increases
Add effective wing area, flight efficiency to greatly improve, had in the various aspects of vertically taking off and landing flyer performance and change greatly very much
It is kind.
Description of the drawings
Fig. 1 is a kind of structural representation of VTOL fixed-wing unmanned plane with the power set that vert of the present utility model
Figure；
Fig. 2 is the carbon fiber spiral paddle structure schematic diagram of the utility model rotor power device.
In figure：
1- fuselages；2- wings；3- support arms；4- rotor power devices；5- empennages；6- ailerons；7- pitots；
401- propeller hubs；402- blades；403- engines.
Specific embodiment
Below in conjunction with the accompanying drawings with embodiment to a kind of VTOL with the power set that vert described in the utility model
Fixed-wing unmanned plane is realized being taken off/being landed with zero velocity, possesses hovering ability, and horizontal flight is entered in the way of fixed wing aircraft
Row is further illustrated.
As shown in figure 1, the utility model provides a kind of VTOL fixed-wing unmanned plane with the power set that vert, bag
Include fuselage 1, wing 2, support arm 3, rotor power device 4 and empennage 5.
Described fuselage 1 is conventional fixed wing aircraft layout with wing 2.
Described fuselage 1 is hollow housing structure, and fuselage interior arranges cargo compartment, air environment, battery and beam
And reinforcing frame；Described air environment includes flight control panel, electron speed regulator and sensing data terminal etc.；Described
Battery is polymer Li-ion battery；Fuselage side is the mounting interface of wing, has the hatch with hatchcover below fuselage, for machine
Carry the dismounting and maintenance, the handling of goods of electronic equipment；The front portion of fuselage 1 is provided with pitot 7, to measure the motion of unmanned plane
Speed；The afterbody of fuselage 1 is provided with one group of rotor power device 4, and for unmanned plane during flying forward thrust is provided.
Described wing 2 is fixed-wing aerofoil profile, hollow type structure, inside arrangement rib and girder construction, below the middle part of wing 2
There is opening, for installing the digital rudder controller that aileron 6 is used is manipulated；A piece support arm 3 is respectively installed below the wing of both sides, two are propped up
The afterbody of brace 3 is fixedly connected empennage 5, and fuselage 1 is connected by support arm 3 with empennage 5.
Described support arm 3 is fuselage connection, connection fuselage 1 and empennage 5；Four groups of rotations are symmetrically installed on support arm 3
Wing power set 4, wherein two groups of rotor power devices 4 are located at the leading edge of support arm 3, constitute it is described in the utility model vert it is dynamic
Power apparatus system, by verting, structure can be verted with 90 degree, i.e., from being tilted to and the upright position of wing 2 with the horizontal level of wing 2；
Other two groups of rotor power devices 4 are located between wing 2 and empennage 5 on support arm；In the geometry of four groups of rotor power devices 4
The heart overlaps with the position of centre of gravity of whole unmanned plane, the horizontal thrust after providing the lift of VTOL and its vert for unmanned plane.
Move five groups of described rotor power devices 4, part when lift when VTOL is provided for unmanned plane and cruise
Power；Every group of rotor power device 4 includes a brushless electric machine and a carbon fiber spiral oar, and described brushless electric machine is outer rotor
Brshless DC motor, is fixed on the support arm 3 of the lower section of wing 2 or fuselage 1 using screw, is controlled by air environment
System, by battery the energy is provided；Described carbon fiber spiral oar includes propeller hub 401, blade 402 and engine 403, as shown in Figure 2.
Described empennage 5 is as shown in Figure 1 reverse V-shaped.
A kind of VTOL fixed-wing unmanned plane with the power set that vert described in the utility model realizes that flight is appointed
The detailed process of business is as follows：
(1) instruction of taking off is given, by four rotor power devices 4 on support arm 3 lift is provided, realize taking off vertically；
(2) reach after certain altitude, under the instruction of flight control panel, control the deflection of two rotors of the front side of wing 2
Angle, the rotating speed of adjustment two rotors of rear side balances the vertical lift that before and after two pairs of rotors are provided, and opens the rotation of the afterbody of fuselage 1
Wing power set 4 are to increase horizontal thrust, while controlling the deflection angle of empennage 5 so that unmanned plane is proceeded to by floating state and patrolled
Boat state of flight, by wing 2 more lift are provided, and the flight efficiency of cruise are improved, into airline operation.
Claims (2)
1. a kind of VTOL fixed-wing unmanned plane with the power set that vert, it is characterised in that：Including fuselage, wing, prop up
Brace, rotor power device and empennage；
Described fuselage is fixed wing aircraft layout with wing；
Described fuselage is hollow housing structure, and fuselage interior arranges cargo compartment, air environment, battery and beam and reinforcement
Frame；Described air environment includes flight control panel, electron speed regulator and sensing data terminal；Described battery is poly-
Compound lithium ion battery；Fuselage side is the mounting interface of wing, has the hatch with hatchcover below fuselage；The anterior installation of fuselage
There is pitot；One group of rotor power device is installed on afterbody；
Described wing is fixed-wing aerofoil profile, and wing is hollow type structure, inside arrangement rib and girder construction；In unmanned plane both sides
Wing lower section is respectively installed by a piece support arm；The afterbody of two support arms is fixedly connected empennage；
Four groups of rotor power devices are symmetrically installed on described support arm, wherein two groups of rotor power devices are located at before support arm
Edge, constitutes the power set that vert described in the utility model, and in addition two groups of rotor power devices are located between wing and empennage
On support arm；The geometric center of four groups of rotor power devices overlaps with the position of centre of gravity of whole unmanned plane；
Described empennage is reverse V-shaped.
2. a kind of VTOL fixed-wing unmanned plane with the power set that vert according to claim 1, its feature exists
In：Described rotor power device includes a brushless electric machine and a carbon fiber spiral oar；Described brushless electric machine turns for outer
Sub- brshless DC motor, on the support arm being fixed on below wing using screw or fuselage, is controlled by air environment,
The energy is provided by battery；Described carbon fiber spiral oar includes propeller hub, blade and engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621167766.XU CN206125423U (en) | 2016-11-02 | 2016-11-02 | VTOL fixed wing uavs with power device verts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621167766.XU CN206125423U (en) | 2016-11-02 | 2016-11-02 | VTOL fixed wing uavs with power device verts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206125423U true CN206125423U (en) | 2017-04-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621167766.XU Expired - Fee Related CN206125423U (en) | 2016-11-02 | 2016-11-02 | VTOL fixed wing uavs with power device verts |
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| CN107253527A (en) * | 2017-05-08 | 2017-10-17 | 西安多杰机器人有限公司 | One kind can take off vertically compound fixed-wing unmanned plane |
| CN107264794A (en) * | 2017-06-09 | 2017-10-20 | 北京航空航天大学 | A kind of control method of detachable hybrid driving VUAV |
| CN107336833A (en) * | 2017-07-05 | 2017-11-10 | 天津曙光天成科技有限公司 | A kind of compound unmanned plane and control method |
| CN107600414A (en) * | 2017-09-11 | 2018-01-19 | 珠海天晴航空航天科技有限公司 | A kind of unmanned plane that can be taken off and quickly be assembled without instrument in case |
| CN107878746A (en) * | 2017-10-20 | 2018-04-06 | 西北工业大学 | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic |
| CN107953984A (en) * | 2017-11-29 | 2018-04-24 | 北京航空航天大学 | A kind of easy-to-mount reverse V-shaped empennage connection structure |
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| CN108341052A (en) * | 2018-02-13 | 2018-07-31 | 北京航空航天大学 | Composite rotor aircraft |
| CN108341050A (en) * | 2017-12-06 | 2018-07-31 | 广东康云多维视觉智能科技有限公司 | A kind of multiple propeller unmanned plane |
| CN108408042A (en) * | 2018-04-12 | 2018-08-17 | 中国计量大学 | A kind of tiltrotor with deformable wing |
| CN108820203A (en) * | 2018-05-29 | 2018-11-16 | 中山星图航空航天技术有限公司 | A kind of unmanned plane and flight control system of tilting type VTOL fixed-wing |
| CN108910049A (en) * | 2018-05-23 | 2018-11-30 | 深圳智航无人机有限公司 | Unmanned plane and UAV system for logistics transportation |
| WO2019010554A1 (en) * | 2017-07-10 | 2019-01-17 | Rodrigues Tiago Giglio | Remotely piloted aircraft |
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| CN107264794A (en) * | 2017-06-09 | 2017-10-20 | 北京航空航天大学 | A kind of control method of detachable hybrid driving VUAV |
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| CN107600414B (en) * | 2017-09-11 | 2024-03-15 | 珠海天晴航空航天科技有限公司 | Unmanned aerial vehicle capable of taking off in box and rapidly assembling without tools |
| CN107878746A (en) * | 2017-10-20 | 2018-04-06 | 西北工业大学 | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic |
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| CN110466750A (en) * | 2019-08-19 | 2019-11-19 | 西北工业大学 | A kind of Portable vertical landing scouting monitoring unmanned plane |
| CN112810812A (en) * | 2021-01-25 | 2021-05-18 | 西北工业大学 | Combined type VTOL long-endurance electric unmanned aerial vehicle |
| CN113120231A (en) * | 2021-06-01 | 2021-07-16 | 合肥工业大学 | Fixed wing forest fire control scouting hits unmanned aerial vehicle |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170426 Termination date: 20211102 |